Check patentability & draft patents in minutes with Patsnap Eureka AI!

Design Method of Low Pressure Turbine Rear Axle

A low-pressure turbine and design method technology, applied in the direction of turbine/propulsion device lubrication, engine lubrication, engine components, etc., can solve problems such as poor sealing effect

Active Publication Date: 2016-02-24
NORTHWESTERN POLYTECHNICAL UNIV
View PDF8 Cites 2 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to overcome the deficiency of poor sealing effect at the radial interference fit between the matching surface of the front extension section of the existing low-pressure turbine rear axle and the sealing runway matching surface, the present invention provides a low-pressure turbine rear axle

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Design Method of Low Pressure Turbine Rear Axle
  • Design Method of Low Pressure Turbine Rear Axle
  • Design Method of Low Pressure Turbine Rear Axle

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0037] Embodiment 1: the low-pressure turbine rear axle is the axis formed by the low-pressure turbine rear journal 2, the inclined transition section 3, the rear extension sealing runway 5, the vertical transition section 7, the sealing grate teeth 9, and the front extension section 10. The hollow disk part of the center of gyration 1 has oil passage holes 4 uniformly distributed along the circumferential direction above the inclined transition section 3, and vent holes 6 uniformly distributed along the circumferential direction are opened at the root of the vertical transition section 7, and above the vertical transition section 7 There are bolt holes 8 evenly distributed along the circumferential direction, and riveting pin holes 14 evenly distributed along the circumferential direction are opened on the vertical section of the front extension section 10 . The front extension mating surface 15 is a conical surface with a taper of 1:19.9643, which corresponds to an equivalent...

Embodiment 2

[0039] Embodiment 2: the low-pressure turbine rear axle is the axis formed by the low-pressure turbine rear journal 2, the inclined transition section 3, the rear extension sealing runway 5, the vertical transition section 7, the sealing grate teeth 9, and the front extension section 10. The hollow disk part of the center of gyration 1 has oil passage holes 4 uniformly distributed along the circumferential direction above the inclined transition section 3, and vent holes 6 uniformly distributed along the circumferential direction are opened at the root of the vertical transition section 7, and above the vertical transition section 7 There are bolt holes 8 evenly distributed along the circumferential direction, and riveting pin holes 14 evenly distributed along the circumferential direction are opened on the vertical section of the front extension section 10 . The front extension mating surface 15 is a conical surface with a taper of 1:24.8403, which corresponds to an equivalent...

Embodiment 3

[0041] Embodiment 3: Optimum design of the rear shaft of the low-pressure turbine by applying the method of the present invention and keeping the geometric feature that the angle between the front extension section chamfer and the axial direction y is 45 degrees.

[0042] Step 1. Establish an equivalent simplified model of the assembly of the low-pressure turbine rear axle and the sealed runway in the commercial finite element software ANSYS. Assuming that the connection strength of the riveted pins meets the engineering requirements, the joints of the riveted pins are firmly connected, ignoring the oil flow Holes, air holes, bolt holes, riveting pin holes and sealing grate tooth structure, the assembly is simplified into an axisymmetric two-dimensional plane model, and the radial coordinates of the mating surface of the front extension section are used when modeling Δ=0.1mm smaller than the radial coordinate of the sealing runway matching surface to simulate the radial interfe...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The invention discloses a low-pressure turbine rear shaft and the design method thereof to solve the technical problem of an existing low-pressure turbine rear shaft that the sealing performance of the position where a front extension section matching surface is in radial interference fit with an obturage runway matching surface is poor. According to the technical scheme, the front extension section matching surface is a conical surface and corresponds to an equivalently simplified axial symmetry two-dimensional planar structure, the cross section of the front extension section matching surface is a line segment which is formed by connection of the left end point of the cross section of the front extension section matching surface and a right end point of the cross section of the front extension section matching surface and becomes lower from left to right in the axial direction, and the interference magnitude of the position where the front extension section matching surface is in radial interference fit with the obturage runway matching surface becomes larger gradually from left to right in the axial direciton. Due to the fact that the front extension section matching surface is the conical surface, the distribution of radial displacement of the front extension section matching surface and the distribution of radial displacement of the obturage runway matching surface are balanced, no gap is generated at the position where the front extension section matching surface is in radial interference fit with the obturage runway matching surface during working, and the sealing effect of an obturage runway is improved.

Description

technical field [0001] The invention relates to a low-pressure turbine rear shaft, and also relates to a design method of the low-pressure turbine rear shaft. Background technique [0002] refer to Figure 1~3 , the document "Chen Guang, Hong Jie, Ma Yanhong. Aviation Gas Turbine Engine Structure [M]. Beijing: Beijing University of Aeronautics and Astronautics Press, 2010." discloses a low-pressure turbine rear axle, which is composed of a low-pressure turbine rear axle The shaft journal 2, the inclined transition section 3, the rear extended sealing runway 5, the vertical transition section 7, the sealing grate teeth 9 and the front extension section 10 constitute a hollow disc-shaped part whose axis is the center of rotation 1, and the inclined transition section 3 There are oil passage holes 4 uniformly distributed along the circumferential direction on the top, vent holes 6 uniformly distributed along the circumferential direction are opened on the root of the vertical t...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/06
Inventor 张卫红牛草罗雅文张治东王冰旭
Owner NORTHWESTERN POLYTECHNICAL UNIV
Features
  • R&D
  • Intellectual Property
  • Life Sciences
  • Materials
  • Tech Scout
Why Patsnap Eureka
  • Unparalleled Data Quality
  • Higher Quality Content
  • 60% Fewer Hallucinations
Social media
Patsnap Eureka Blog
Learn More

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2025 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com